Analysis of Correction of the Trajectory of Launching a Spacecraft into High Circular Orbits of an Artificial Moon Satellite Using a Two-Impulse Transfer
摘要
Abstract
The correction of the trajectory of a two-impulse launch of a spacecraft into a high circular orbit of an artificial Moon satellite is considered, taking into account errors in determining the position and speed of the satellite, as well as errors in issuing speed impulses in magnitude and direction. Trajectory corrections with one and two correction impulses are considered. Results of analysis are presented. Conclusions are drawn about the practical application of such trajectories.